Component comprising a multiplicity of cooling passages

Abstract

A component comprises a multiplicity of cooling passages arranged in two intersecting arrays to form a multiplicity of cooling passage intersections. Air jet interactions are generated at cooling passage intersections when air is passed through the cooling passages. The spacing of the passages in at least one of the arrays is chosen to provide a predetermined range of intersection density in a selected region or regions of the component.

1. A component comprises a multiplicity of cooling passages arranged in two intersecting arrays to form a multiplicity of cooling passage intersections, such that when air is passed through said cooling passages, air jet interactions are generated at said cooling passage intersections wherein the spacing of the passages in at least one of the arrays is chosen to provide a predetermined range of intersection density in a selected region or regions of the component,
 a first array of the two intersecting arrays having passages arranged in a first pattern, and a second array having passages arranged in a second pattern different than the first pattern. 
 
   
   
     2. A component as claimed in  claim 1  wherein at least one of the arrays is fan shaped. 
   
   
     3. A component as claimed in  claim 1  wherein at least one of the arrays comprises parallel cooling passages. 
   
   
     4. A component as claimed in  claim 1  wherein the pitch of at least one of the arrays is constant. 
   
   
     5. A component as claimed in  claim 1  wherein the cooling passages intersect at an included angle of at least 10 degrees. 
   
   
     6. A component as claimed in  claim 1  wherein the cooling passages are substantially straight. 
   
   
     7. A component as claimed in  claim 1  wherein the cooling passages are substantially coplanar. 
   
   
     8. A component as claimed in  claim 1  wherein at least one of the cooling passages has a circular cross-section. 
   
   
     9. A component having a cooling arrangement as claimed in  claim 1  where the cooling arrangement is provided in a turbine aerofoil for a gas turbine engine. 
   
   
     10. A component as claimed in  claim 9  wherein the cooling arrangement is provided in at least a trailing edge of the turbine aerofoil. 
   
   
     11. A component as claimed in  claim 10  wherein the cooling arrangement is provided in at least a leading edge of the turbine aerofoil. 
   
   
     12. A component as claimed in  claim 1 , wherein the first pattern and the second pattern are substantially identical with the passages of the first array having diameters different than diameters of the passages of the second array. 
   
   
     13. A component as claimed in  claim 1 , wherein the first pattern and the second pattern are substantially identical with the passages arranged in the first pattern converging in a first direction, and the passages arranged in the second pattern diverging in the first direction. 
   
   
     14. A component as claimed in  claim 1 , wherein the passages of the first array has a different spacing from the passages of the second array.